Lift-to-Drag Ratio given required Thrust of Aircraft Calculator

✖Weight of Body is the force acting on the object due to gravity.ⓘ Weight of Body [W_body]			+10% -10%
✖The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.ⓘ Thrust [T]			+10% -10%

✖The Lift-to-Drag ratio is the amount of lift generated by a wing or vehicle, divided by the aerodynamic drag it creates by moving through the air.ⓘ Lift-to-Drag Ratio given required Thrust of Aircraft [LD]

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Lift-to-Drag Ratio given required Thrust of Aircraft Solution

STEP 0: Pre-Calculation Summary

Formula Used

Lift-to-Drag Ratio = Weight of Body/Thrust
LD = W_body/T
This formula uses 3 Variables

Variables Used

Lift-to-Drag Ratio - The Lift-to-Drag ratio is the amount of lift generated by a wing or vehicle, divided by the aerodynamic drag it creates by moving through the air.
Weight of Body - (Measured in Newton) - Weight of Body is the force acting on the object due to gravity.
Thrust - (Measured in Newton) - The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.

STEP 1: Convert Input(s) to Base Unit

Weight of Body: 221 Newton --> 221 Newton No Conversion Required
Thrust: 100 Newton --> 100 Newton No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

LD = W_body/T --> 221/100

Evaluating ... ...

LD = 2.21

STEP 3: Convert Result to Output's Unit

2.21 --> No Conversion Required

FINAL ANSWER

2.21 <-- Lift-to-Drag Ratio

(Calculation completed in 00.004 seconds)

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Created by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

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PSG College of Technology (PSGCT), Coimbatore

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< Lift and Drag Requirements Calculators

Lift for Unaccelerated Flight

LaTeX Go Lift Force = Weight of Body-Thrust*sin(Thrust Angle)

Drag for Level and Unaccelerated Flight at Negligible Thrust Angle

LaTeX Go Drag Force = Dynamic Pressure*Area*Drag Coefficient

Lift for Level and Unaccelerated Flight at Negligible Thrust Angle

LaTeX Go Lift Force = Dynamic Pressure*Area*Lift Coefficient

Drag for Level and Unaccelerated Flight

LaTeX Go Drag Force = Thrust*cos(Thrust Angle)

Lift-to-Drag Ratio given required Thrust of Aircraft Formula

LaTeX Go

Lift-to-Drag Ratio = Weight of Body/Thrust
LD = W_body/T

How to determine the lift-to-drag ratio?

The Lift-to-drag ratio for an aircraft can be determined by flight test, by calculation, or by testing in a wind tunnel.

How to Calculate Lift-to-Drag Ratio given required Thrust of Aircraft?

Lift-to-Drag Ratio given required Thrust of Aircraft calculator uses Lift-to-Drag Ratio = Weight of Body/Thrust to calculate the Lift-to-Drag Ratio, The Lift-to-Drag Ratio given required Thrust of Aircraft is a measure used in aerodynamics to assess the efficiency of an aircraft's wing design, it is defined as the ratio of the lift generated by the wings to the drag produced by the aircraft as it moves through the air. Lift-to-Drag Ratio is denoted by LD symbol.

How to calculate Lift-to-Drag Ratio given required Thrust of Aircraft using this online calculator? To use this online calculator for Lift-to-Drag Ratio given required Thrust of Aircraft, enter Weight of Body (W_body) & Thrust (T) and hit the calculate button. Here is how the Lift-to-Drag Ratio given required Thrust of Aircraft calculation can be explained with given input values -> 2.21 = 221/100.

FAQ

What is Lift-to-Drag Ratio given required Thrust of Aircraft?

The Lift-to-Drag Ratio given required Thrust of Aircraft is a measure used in aerodynamics to assess the efficiency of an aircraft's wing design, it is defined as the ratio of the lift generated by the wings to the drag produced by the aircraft as it moves through the air and is represented as LD = W_body/T or Lift-to-Drag Ratio = Weight of Body/Thrust. Weight of Body is the force acting on the object due to gravity & The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.

How to calculate Lift-to-Drag Ratio given required Thrust of Aircraft?

The Lift-to-Drag Ratio given required Thrust of Aircraft is a measure used in aerodynamics to assess the efficiency of an aircraft's wing design, it is defined as the ratio of the lift generated by the wings to the drag produced by the aircraft as it moves through the air is calculated using Lift-to-Drag Ratio = Weight of Body/Thrust. To calculate Lift-to-Drag Ratio given required Thrust of Aircraft, you need Weight of Body (W_body) & Thrust (T). With our tool, you need to enter the respective value for Weight of Body & Thrust and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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